US5445499A - Retaining and sealing system for rotor blades - Google Patents

Retaining and sealing system for rotor blades Download PDF

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Publication number
US5445499A
US5445499A US08/181,104 US18110494A US5445499A US 5445499 A US5445499 A US 5445499A US 18110494 A US18110494 A US 18110494A US 5445499 A US5445499 A US 5445499A
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US
United States
Prior art keywords
disk
sectors
tabs
throat
retaining
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US08/181,104
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English (en)
Inventor
Jean-Louis Charbonnel
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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Assigned to SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION "SNECMA" reassignment SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION "SNECMA" ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CHARBONNEL, JEAN-LOUIS
Application granted granted Critical
Publication of US5445499A publication Critical patent/US5445499A/en
Assigned to SNECMA MOTEURS reassignment SNECMA MOTEURS CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SOCIETE NATIONALE D'ETUDES ET DE CONSTRUCTION DE MOTEURS D'AVIATION
Assigned to SNECMA reassignment SNECMA CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SNECMA MOTEURS
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

  • the invention concerns a system for retaining and sealing vanes engaged in the axial broachings of a rotor disk.
  • Certain turbo-engines have a rotor formed of a disk and vanes provided with feet intended to be engaged in axial or slightly oblique broachings established at the periphery of the disk. It is then vital to provide means to stop the feet from sliding to a position which would obstruct the clearances existing between the feet and the surfaces of the broachings which could constitute bypass passages for the gases which circulate in the turbo-engine, thus resulting in adversely affecting the efficiency of the latter. Therefore, sets of joints or flanges of varied designs have been provided, one example being described in the U.S. Pat. No. 4,846,628. The joints and the flanges are retained against any axial movement by means of grooves or small tongues situated on the vanes and the disk.
  • the main object of the invention is to ensure that the vanes are retained in a simple manner while ensuring good imperviousness.
  • the system used includes a circular sealing flange for vanes having feet slidably engaged in the axial broachings of a rotor disk; the flange is circular and mounted on the disk and in front of one extremity face of the broachings so as to cover the vane feet; it includes an internal sealing lip housed in a circular recess of the disk and one external sealing lip applied on a bearing surface of the vane feet.
  • the system is characterized in that the flange and the vane feet have tabs mutually imbricated and provided with a first throat radially open towards the inside; the disk has a second throat radially open towards the outside and situated in front of the first throat; an elastic joint occupies at least the first throat while being able to be fully driven back into the second throat; in addition, the flange is divided into sectors of a circle, each sector being provided with a projection touching a disk projection via its radially external face, one of the sectors having a smaller width and able to be installed by means of a radial and longitudinal movement between the other sectors; finally, each sector bears one of the tabs and the tabs of the sectors have an angular extension smaller than the spacings between the projections of the disk.
  • the number of the sectors is the same as that of the vanes and the tabs of the sectors then alternate with those of the vane feet.
  • the projections of the sectors are advantageously merged with the tabs of the sectors.
  • the sectors apart from the one of smaller width which is dealt with in a particular way, are firstly placed via a radial movement which introduces their internal lip into the circular recess, thus making the projections and the tabs of the sectors move between the projections of the disk, then by a movement tangential to the disk which makes the projections of the sectors move under the projections of the disk, the outer lips onto the bearing surfaces of the vane feet and places the tabs of the sectors next to the tabs of the vane feet.
  • the flange may include a gasket on the outer lip which touches the bearing surface.
  • FIG. 1 generally represents a longitudinal section of the system
  • FIG. 2 shows the system in more detail with the vanes extracted
  • FIG. 3 shows in detail the system in an assembled state
  • FIG. 4 shows a view in an axial direction of the system during assembling
  • FIGS. 5 and 6 show a perspective view in longitudinal section of one particular stage of assembling.
  • the flange 1 (FIGS. 1 to 3) is a ring divided into sectors 2 (FIG. 4) whose angular extension is uniform and corresponds to a vane implantation pitch, except for a short sector 3 whose flanks 4 are parallel, the short sectors being correlatively framed by two elongated sectors 5 (FIG. 6) whose angular extension is slightly larger than the ordinary sectors 2.
  • the sectors 2, 3 and 5 all have the same section taken in a longitudinal plane formed (FIG.
  • the rotor disk is denoted by the reference 9. It includes a circular recess 10 with the shape of a groove or throat and which in particular comprises a circular bottom bearing surface 11 and a stop bearing surface 12 distanced from the vanes. Surfaces having a shape identical to the internal lip 6 abut against these bearing surfaces and provide one part of the sealing function.
  • the disk 9 further includes (FIG. 4) axial broachings 13 between which bosses 14 extend, a claw coupling projection 15 being established on each boss, as well as a disk throat 23 (FIG. 2) adjacent to the circular recess 10 parallel to it and situated between it and the bosses 14.
  • the disk throat 23 opens outwardly.
  • the vanes are denoted by the reference 16 and composed of a blade 17 which constitutes the effective part of the vane 16, and a foot 18 engaged in a corresponding broaching 13.
  • the feet 18 comprise an arc of a circle projection 19 and forming a pair of bearing surfaces at a right angle intended to complete the sealing function by undergoing the pressure of surfaces having the same disposition of the outer lip 7.
  • the projections 19 are in fact situated on external portions of the feet 18 adjacent to the blades 17; these portions are not engaged on the broachings 13 and surround the bosses 14; they are contiguous and all extend over the entire circumference or almost do (FIG. 4).
  • the vanes 16 also include tabs 20 which extend over arc portions of the feet 18 projecting from the bottom of the broachings 13 towards the sectors 2, 3 and 5.
  • the tabs 8 and 20 overlap each other; throat portions, respectively 21 and 22, which they bear, extend so as to form a single throat (which moreover may be discontinuous along the actual angular extension of the tabs 8 and 20) and which is also open towards the inside and on the disk throat 23.
  • An elastic circular joint 24 is housed in the throats 21 and 22 and preferably also in one portion of the disk throat 23.
  • the outer surface 25 of the tabs 8 of the flange 1 touches the internal surface 26 of the claw coupling projections 15 and prevents any radial movement of the sectors 2, 3 and 5, and the centrifugal forces created by the rotation of the disk 9 in operation then provokes a movement of rotation around the claw coupling projections 15 of the sectors 2, 3 and 5 whose lips 6 and 7 come to touch the sealing bearing surfaces of the circular recess 10 and steps 19.
  • a lip gasket 27 (FIG. 3) may be placed on the outer lip 7 so as to complete imperviousness by pressing on the bearing surface orientated towards the inside of the step 19.
  • the joint 24 locks both the vanes 16 and the sectors of the flange 1 in an axial direction.
  • the mounting of the system consists first of all of placing the sectors 2 and 5 of the flange 1 and the vanes 16 and more specifically in this embodiment, where there are as many vanes 16 as the sectors 2, 3 and 5, of alternating an insertion of a vane 16 in its broaching 13 and an introduction of a sector 2 or 5 effected via a radial movement so as to place it on the disk 9 and place the extremity of its internal lip 6 in the circular recess 10 but near its definitive position so that its tab 8 passes in front of a broaching 13, still empty, between consecutive claw coupling projections 15, and then via an angular movement so as to slide the tab 8 under the claw coupling projection 15 which shall retain it and until the tab 8 arrives against the tab 20 of the vane 16 which has just been placed or merely close to it. The movement is continued until the sector 2 or 5 which it undergoes touches the adjacent sector already installed.
  • the method is rather particular and involves movements made carefully in accurately adjusted pieces shown on FIGS. 5 and 6.
  • the short sector 3 is introduced between the elongated sectors 5 via an oblique movement which makes it arrive at the position of FIG. 6 and shown by the dot-and-dash lines on FIG. 5 so that the internal lip 6 is engaged deeply inside the circular recess 10 (which is significantly deeper at this location) and the tab 8' (finer than the other tabs 8 owing to a machining of its internal surface which causes the throat 21 to partly disappear) starts to clear an opening between the associated claw coupling projection 15 and the joint 24.
  • the joint 24 is a particuarly simple effective device of the mobile elements of the system in an axial direction and the assembling of the flange 1 is relatively short and simple.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Applications Or Details Of Rotary Compressors (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Devices (AREA)
US08/181,104 1993-01-27 1994-01-13 Retaining and sealing system for rotor blades Expired - Lifetime US5445499A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9300768 1993-01-27
FR9300768A FR2700807B1 (fr) 1993-01-27 1993-01-27 Système de rétention et d'étanchéité d'aubes engagées dans des brochages axiaux d'un disque de rotor.

Publications (1)

Publication Number Publication Date
US5445499A true US5445499A (en) 1995-08-29

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US08/181,104 Expired - Lifetime US5445499A (en) 1993-01-27 1994-01-13 Retaining and sealing system for rotor blades

Country Status (3)

Country Link
US (1) US5445499A (fr)
FR (1) FR2700807B1 (fr)
GB (1) GB2274688B (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5640081A (en) * 1994-05-13 1997-06-17 Apple Computer, Inc. Method and apparatus for monitoring discharge of a battery device based on battery self-discharge and discharge over time
US6398500B2 (en) 1999-12-20 2002-06-04 General Electric Company Retention system and method for the blades of a rotary machine
EP1018594A3 (fr) * 1999-01-06 2002-07-24 General Electric Company Couvercle pour le rotor d'une turbine
US20040184917A1 (en) * 2001-06-14 2004-09-23 Gerhard Brueckner Fastening of blades
US20050129525A1 (en) * 2002-06-11 2005-06-16 Bekrenev Igor A. Sealing arrangement for a rotor of a turbo machine
US20050265849A1 (en) * 2004-05-28 2005-12-01 Melvin Bobo Turbine blade retainer seal
US20070183894A1 (en) * 2006-02-08 2007-08-09 Snecma Turbomachine rotor wheel
US20100166563A1 (en) * 2007-08-08 2010-07-01 Alstom Technology Ltd Method for improving the sealing on rotor arrangements
CN102128056A (zh) * 2010-01-19 2011-07-20 通用电气公司 密封板和轮叶保持销组件
US20120034087A1 (en) * 2009-03-31 2012-02-09 Siemens Aktiengeselischaft Axial Turbomachine Rotor Having a Sealing Plate
US8128371B2 (en) 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
DE102005017148B4 (de) * 2004-04-15 2014-08-14 General Electric Co. Drehdichtungsanordnung für Kühlkreisläufe von Turbinenschaufeln
US9140136B2 (en) 2012-05-31 2015-09-22 United Technologies Corporation Stress-relieved wire seal assembly for gas turbine engines
US20170226875A1 (en) * 2014-09-30 2017-08-10 Safran Aircraft Engines Mobile vane for a turbine engine, comprising a lug engaging in a locking notch of a rotor disk
KR102127429B1 (ko) * 2019-06-05 2020-06-26 두산중공업 주식회사 터빈 로터 디스크와 인터스테이지 디스크 사이의 실링 구조
US11319824B2 (en) * 2018-05-03 2022-05-03 Siemens Energy Global GmbH & Co. KG Rotor with centrifugally optimized contact faces

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2294732A (en) * 1994-11-05 1996-05-08 Rolls Royce Plc Integral disc seal for turbomachine
DE19507673C2 (de) * 1995-03-06 1997-07-03 Mtu Muenchen Gmbh Leitrad für Turbomaschinen
DE102005059084A1 (de) * 2005-12-10 2007-06-14 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
FR2905139B1 (fr) * 2006-08-25 2012-09-28 Snecma Aube de rotor d'une turbomachine
FR3011031B1 (fr) * 2013-09-25 2017-12-29 Herakles Ensemble rotatif pour turbomachine
EP3061916A1 (fr) * 2015-02-24 2016-08-31 Siemens Aktiengesellschaft Agencement de disque de rotor et procédé de montage d'un agencement de disque de rotor
WO2018132084A1 (fr) * 2017-01-10 2018-07-19 Siemens Aktiengesellschaft Rotor et turbomachine
DE102022134909A1 (de) * 2022-12-28 2024-07-04 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe für ein Gasturbinentriebwerk und Verfahren zur Befestigung einer Schaufelhalteplatte an einer Rotorscheibe eines Gasturbinentriebwerks

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1319587A (fr) * 1961-04-10 1963-03-01 Thomson Houston Comp Francaise Dispositif d'étanchéité et de blocage d'aubes de turbine à longue queue
US3397865A (en) * 1966-09-13 1968-08-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
GB1491480A (en) * 1975-07-28 1977-11-09 Rolls Royce Fixing blades for fluid flow machines
GB2095763A (en) * 1980-12-29 1982-10-06 Rolls Royce Enhancing turbine blade coolant seal force
US4432555A (en) * 1979-02-21 1984-02-21 Rolls Royce Limited Centrifugal seal with deformable frustoconical sealing ring
US4470757A (en) * 1982-02-25 1984-09-11 United Technologies Corporation Sideplate retention for a turbine rotor
US4854821A (en) * 1987-03-06 1989-08-08 Rolls-Royce Plc Rotor assembly
US5330324A (en) * 1992-09-09 1994-07-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Annular gasket disposed at one axial extremity of a rotor and covering blade feet

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4444544A (en) * 1980-12-19 1984-04-24 United Technologies Corporation Locking of rotor blades on a rotor disk
US4846628A (en) * 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1319587A (fr) * 1961-04-10 1963-03-01 Thomson Houston Comp Francaise Dispositif d'étanchéité et de blocage d'aubes de turbine à longue queue
US3397865A (en) * 1966-09-13 1968-08-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
GB1491480A (en) * 1975-07-28 1977-11-09 Rolls Royce Fixing blades for fluid flow machines
US4432555A (en) * 1979-02-21 1984-02-21 Rolls Royce Limited Centrifugal seal with deformable frustoconical sealing ring
GB2095763A (en) * 1980-12-29 1982-10-06 Rolls Royce Enhancing turbine blade coolant seal force
US4470757A (en) * 1982-02-25 1984-09-11 United Technologies Corporation Sideplate retention for a turbine rotor
US4854821A (en) * 1987-03-06 1989-08-08 Rolls-Royce Plc Rotor assembly
US5330324A (en) * 1992-09-09 1994-07-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Annular gasket disposed at one axial extremity of a rotor and covering blade feet

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5640081A (en) * 1994-05-13 1997-06-17 Apple Computer, Inc. Method and apparatus for monitoring discharge of a battery device based on battery self-discharge and discharge over time
EP1018594A3 (fr) * 1999-01-06 2002-07-24 General Electric Company Couvercle pour le rotor d'une turbine
US6499945B1 (en) 1999-01-06 2002-12-31 General Electric Company Wheelspace windage cover plate for turbine
KR100776071B1 (ko) * 1999-01-06 2007-11-15 제너럴 일렉트릭 캄파니 커버 플레이트, 터빈 로터와 커버 플레이트의 조합체 및 커버
US6398500B2 (en) 1999-12-20 2002-06-04 General Electric Company Retention system and method for the blades of a rotary machine
US20040184917A1 (en) * 2001-06-14 2004-09-23 Gerhard Brueckner Fastening of blades
US7090468B2 (en) * 2001-06-14 2006-08-15 Mtu Aero Engines Gmbh Fastening of moving turbomachine blades
US7220099B2 (en) * 2002-06-11 2007-05-22 Alstom Technology Ltd. Sealing arrangement for a rotor of a turbo machine
US20050129525A1 (en) * 2002-06-11 2005-06-16 Bekrenev Igor A. Sealing arrangement for a rotor of a turbo machine
DE102005017148B4 (de) * 2004-04-15 2014-08-14 General Electric Co. Drehdichtungsanordnung für Kühlkreisläufe von Turbinenschaufeln
FR2870884A1 (fr) * 2004-05-28 2005-12-02 Gen Electric Joint d'etancheite pour dispositifs de retenue d'aubages de turbines
US7238008B2 (en) * 2004-05-28 2007-07-03 General Electric Company Turbine blade retainer seal
US20050265849A1 (en) * 2004-05-28 2005-12-01 Melvin Bobo Turbine blade retainer seal
US20070183894A1 (en) * 2006-02-08 2007-08-09 Snecma Turbomachine rotor wheel
US8038403B2 (en) * 2006-02-08 2011-10-18 Snecma Turbomachine rotor wheel
US8128371B2 (en) 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
US9435213B2 (en) * 2007-08-08 2016-09-06 General Electric Technology Gmbh Method for improving the sealing on rotor arrangements
US20100166563A1 (en) * 2007-08-08 2010-07-01 Alstom Technology Ltd Method for improving the sealing on rotor arrangements
US20120034087A1 (en) * 2009-03-31 2012-02-09 Siemens Aktiengeselischaft Axial Turbomachine Rotor Having a Sealing Plate
US8920121B2 (en) * 2009-03-31 2014-12-30 Siemens Aktiengesellschaft Axial turbomachine rotor having a sealing disk
CN102128056A (zh) * 2010-01-19 2011-07-20 通用电气公司 密封板和轮叶保持销组件
US9140136B2 (en) 2012-05-31 2015-09-22 United Technologies Corporation Stress-relieved wire seal assembly for gas turbine engines
US20170226875A1 (en) * 2014-09-30 2017-08-10 Safran Aircraft Engines Mobile vane for a turbine engine, comprising a lug engaging in a locking notch of a rotor disk
US10787915B2 (en) * 2014-09-30 2020-09-29 Safran Aircraft Engines Mobile vane for a turbine engine, comprising a lug engaging in a locking notch of a rotor disk
US11319824B2 (en) * 2018-05-03 2022-05-03 Siemens Energy Global GmbH & Co. KG Rotor with centrifugally optimized contact faces
KR102127429B1 (ko) * 2019-06-05 2020-06-26 두산중공업 주식회사 터빈 로터 디스크와 인터스테이지 디스크 사이의 실링 구조
US11111803B2 (en) 2019-06-05 2021-09-07 Doosan Heavy Industries & Construction Co., Ltd. Sealing structure between turbine rotor disk and interstage disk

Also Published As

Publication number Publication date
GB9401470D0 (en) 1994-03-23
FR2700807A1 (fr) 1994-07-29
FR2700807B1 (fr) 1995-03-03
GB2274688A (en) 1994-08-03
GB2274688B (en) 1996-04-24

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